UAV with wing-plate assemblies providing efficient vertical takeoff and landing capability

Abstract

A technique is directed to operating an unmanned aerial vehicle (UAV) having a fuselage defining a flight direction of the UAV and wing-plate assemblies that propel the UAV in the flight direction defined by the fuselage. The technique involves providing, while the flight direction defined by fuselage of the UAV points vertically from a takeoff location on the ground, thrust from propulsion units of the wing-plate assemblies to fly the UAV along a vertical takeoff path. The technique further involves maneuvering, after the UAV flies along the vertical takeoff path, the UAV to align the flight direction along a horizontal flight path that is perpendicular to the vertical takeoff path. The technique further involves providing, after the UAV flies along the horizontal flight path, thrust from the propulsion units of the wing-plate assemblies to land the UAV along a vertical landing path that is perpendicular to the horizontal flight path.

What is claimed is: 
     
       1. An unmanned aerial vehicle (UAV), comprising:
 a fuselage; 
 primary wings extending from the fuselage and providing lift to the UAV while the UAV is in horizontal flight; and 
 wing-plate assemblies that extend from the primary wings, each wing-plate assembly including a set of propulsion units, each propulsion unit including (i) a housing, (ii) a motor disposed within that housing, and (iii) a propeller coupled to that motor; 
 wherein each propulsion unit further includes:
 a rechargeable battery, the rechargeable battery being constructed and arranged to i) store enough power to solely power the motor of that propulsion unit during vertical takeoff, and ii) recharge during horizontal flight of the UAV from a separate and independent main propulsion unit that maintains horizontal flight of the UAV. 
 
 
     
     
       2. A UAV as in  claim 1  wherein the housing of at least one propulsion unit defines a shroud that partially encloses a propeller, the housing and the propeller forming a shrouded propeller unit. 
     
     
       3. A UAV as in  claim 1 , further comprising:
 wherein the main propulsion unit includes a fuel tank, an engine, and a main propeller, the engine driving the main propeller and consuming fuel from the fuel tank during horizontal flight; and 
 wherein the main propulsion unit is constructed and arranged to recharge the rechargeable batteries during horizontal flight. 
 
     
     
       4. A UAV as in  claim 1 , further comprising:
 wherein the main propulsion unit includes a fuel tank, an engine, and a main propeller, the engine driving the main propeller and consuming fuel from the fuel tank during horizontal flight; and 
 wherein the set of propulsion units in each one of the wing-plate assemblies comprises a plurality of propulsion units. 
 
     
     
       5. A UAV as in  claim 1 , wherein the main propulsion unit that is separate and independent from the propulsion units provides sufficient thrust to maintain horizontal flight of the UAV. 
     
     
       6. A UAV as in  claim 1  wherein the wing-plate assemblies provide lift to the UAV during vertical flight. 
     
     
       7. A UAV as in  claim 6  wherein the propeller of each propulsion unit is a foldable propeller assembly; and wherein the UAV further comprises:
 a controller which directs the foldable propeller assembly of each propulsion unit to fold following attainment of horizontal flight by the UAV. 
 
     
     
       8. A UAV as in  claim 1  wherein the primary wings include:
 a left wing having a proximal end that attaches to a left side of the fuselage and a distal end, and 
 a right wing having a proximal end that attaches to a right side of the fuselage and a distal end; and 
 wherein the wing-plate assemblies include:
 a left wing-plate assembly that attaches to the distal end of the left wing, and 
 a right wing-plate assembly that attaches to the distal end of the right wing. 
 
 
     
     
       9. A UAV as in  claim 8  wherein the left wing extends from the left side of the fuselage;
 wherein the right wing extends from the right side of the fuselage; 
 wherein the left wing-plate assembly extends from the distal end of the left wing; 
 wherein the right wing-plate assembly extends from the distal end of the right wing; and 
 wherein the left and right wing-plate assemblies support the left and right wings above a flat surface such that the left and right wings are free of contacting the flat surface while the UAV is aimed in a vertical direction and sits on the flat surface. 
 
     
     
       10. A UAV as in  claim 9  wherein each wing-plate assembly further includes:
 a set of wing-plate control surfaces which is constructed and arranged to provide angular deflection and receive an airstream from the set of propulsion units of that wing-plate assembly. 
 
     
     
       11. A UAV as in  claim 9  wherein the wing-plate assemblies further include:
 respective sets of wheels constructed and arranged to roll over the flat surface, the respective sets of wheels providing mobility to the UAV while the UAV is not in flight. 
 
     
     
       12. A UAV as in  claim 1  wherein the rechargeable battery of each propulsion unit is housed within the housing of that propulsion unit. 
     
     
       13. A UAV as in  claim 12 , further comprising:
 wherein the main propulsion unit includes a fuel tank, an engine, and a main propeller, the engine driving the main propeller and consuming fuel from the fuel tank during horizontal flight; and 
 wherein the main propulsion unit is constructed and arranged to recharge the rechargeable battery of each propulsion unit during horizontal flight. 
 
     
     
       14. A UAV as in  claim 13 , further comprising:
 a parachute assembly disposed within the fuselage, the parachute assembly being constructed and arranged to deploy a parachute in the event the propulsion units and the main propulsion assembly are unable to provide sufficient lift to safely land the UAV. 
 
     
     
       15. A UAV as in  claim 13 , further comprising:
 a set of ancillary propulsion units disposed along a leading edge of each primary wing; and 
 wherein all of the propulsion units and the main propulsion assembly are constructed and arranged to provide at least 800 pounds of combined lift during takeoff. 
 
     
     
       16. A UAV as in  claim 1  wherein the set of propulsion units of each wing-plate assembly provides vertical lift to the UAV during takeoff, the vertical lift moving and controlling the UAV along a vertical takeoff path while the UAV takes off. 
     
     
       17. A UAV as in  claim 16  wherein the sets of propulsion units of the wing-plate assemblies provide UAV rotation to the UAV following takeoff and before horizontal flight, the UAV rotation biasing the UAV through a rotational maneuver that transitions the UAV from a vertical orientation to a horizontal orientation. 
     
     
       18. A UAV as in  claim 1  wherein the set of propulsion units of each wing-plate assembly provides vertical lift to the UAV during landing, the vertical lift slowing the rate of descent of the UAV and controlling the UAV along a vertical landing path while the UAV lands. 
     
     
       19. A UAV as in  claim 18  wherein the sets of propulsion units of the wing-plate assemblies provide pitch, directional control, and UAV rotation to the UAV following horizontal flight and before landing, the UAV rotation biasing the UAV through a rotational maneuver that transitions the UAV from a horizontal orientation to a vertical orientation. 
     
     
       20. A method of operating an unmanned aerial vehicle (UAV) having (i) a fuselage defining a flight direction of the UAV and (ii) wing-plate assemblies that propel the UAV in the flight direction defined by the fuselage, each wing plate assembly including a set of propulsion units, each propulsion unit including (i) a housing, (ii) a motor disposed within that housing, (iii) a propeller coupled to that motor, and (iv) a rechargeable battery, the rechargeable battery being constructed and arranged to i) store enough power to solely power the motor of that propulsion unit during vertical takeoff, and ii) recharge during horizontal flight of the UAV from a separate and independent main propulsion unit that maintains horizontal flight of the UAV, the method comprising:
 while the flight direction defined by fuselage of the UAV points vertically from a takeoff location on the ground, providing thrust from propulsion units of the wing-plate assemblies to fly the UAV along a vertical takeoff path; 
 after the UAV flies along the vertical takeoff path, maneuvering the UAV to align the flight direction defined by fuselage of the UAV along a horizontal flight path that is perpendicular to the vertical takeoff path, and recharging the rechargeable battery of each propulsion unit in the wing-plate assemblies, during horizontal flight of the UAV, from the separate and independent main propulsion unit that maintains horizontal flight of the UAV; and 
 after the UAV flies along the horizontal flight path, providing thrust from the propulsion units of the wing-plate assemblies to land the UAV along a vertical landing path that is perpendicular to the horizontal flight path. 
 
     
     
       21. A method as in  claim 20  wherein providing thrust from the propulsion units of the wing-plate assemblies to fly the UAV along the vertical takeoff path includes:
 using the propulsion units of the wing-plate assemblies to provide vertical lift to the UAV during takeoff, the vertical lift moving the UAV along the vertical takeoff path while the UAV takes off, and 
 using the propulsion units of the wing-plate assemblies to provide UAV rotation to the UAV following takeoff and before horizontal flight, the UAV rotation biasing the UAV through a rotational maneuver that transitions the UAV from a vertical orientation to a horizontal orientation. 
 
     
     
       22. A method as in  claim 21  wherein providing thrust from the propulsion units of the wing-plate assemblies to land the UAV along the vertical landing path that is perpendicular to the horizontal flight path includes:
 using the propulsion units of the wing-plate assemblies to provide UAV rotation and directional control to the UAV following horizontal flight and before landing, the UAV rotation biasing the UAV through a rotational maneuver that transitions the UAV from a horizontal orientation to a vertical orientation, and 
 using the propulsion units of the wing-plate assemblies to provide vertical thrust to the UAV during landing, the vertical thrust slowing the UAV along the vertical landing path while the UAV lands.